Abstract: A turbine engine comprising an engine core, a plurality of circumferentially arranged vanes, and a floating seal. The plurality of circumferentially arranged vanes forming an upper band and a lower band. The floating seal being carried by at least one respective vane of the plurality of circumferentially arranged vanes. The floating seal having a ring and at least one dynamic seal.

Abstract: A turbine engine having an engine core, a first seal structure, a plurality of circumferentially arranged vanes, a plurality of struts, and a second seal structure. The engine core can define a rotor and a stator having a casing. The first seal structure can include a finger seal projecting from the rotor. The plurality of circumferentially arranged vanes can include an uppers band mounted to the casing, and a lower band located radially above the finger seal. At least some of the struts of the plurality of struts can extend through the plurality of circumferentially arranged vanes. The second seal structure can form a seat with the lower band.

Abstract: An airfoil for a gas turbine engine can include an outer surface defining a pressure side and a suction side extending axially between a leading edge and a trailing edge and extending radially between a first end and a second end to define a span-wise direction, and a cooling circuit located within the airfoil. The cooling circuit can include a cooling air inlet passage, a radially extending supply passage, an upstream supply passage fluidly coupling the cooling air inlet passage and the supply passage, and a near wall cooling mesh extending along a portion of the outer surface.

Abstract: A turbine engine comprising an engine core comprising at least a compressor section, a combustor section, and a turbine section and defining a rotor and a stator. The turbine engine further comprising a first seal structure circumferentially extending about the rotor, a plurality of circumferentially arranged vanes, a plurality of struts extending through the vanes, and a second seal structure extending circumferentially about the first seal structure.

Abstract: An airfoil for a gas turbine engine can include an outer surface defining a pressure side and a suction side extending axially between a leading edge and a trailing edge and extending radially between a first end and a second end to define a span-wise direction, and a cooling circuit located within the airfoil. The cooling circuit can include a cooling air inlet passage, a radially extending supply passage, an upstream supply passage fluidly coupling the cooling air inlet passage and the supply passage, and a near wall cooling mesh extending along a portion of the outer surface.

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.

Abstract: A turbine engine can include an airfoil comprising an outer wall bounding an interior, as well as an airfoil cooling circuit located within the interior and including a feed tube separating into at least first and second branches. A flow divider can be included in the airfoil and positioned to confront the feed tube.

Abstract: An apparatus and method for an airfoil for a gas turbine engine includes a trailing edge cooling circuit utilizing a plurality of trailing edge ejection holes. The ejection holes can include a circumferentially radiused inlet, a converging section, a metering section, and a diverging section to improve airfoil cooling as well as castability.

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.

Abstract: An airfoil for a gas turbine engine comprises a cooling circuit defined within the airfoil providing a flow of cooling fluid within the airfoil. The cooling circuit exhausts the flow of cooling fluid out a slot opening comprising an airfoil element. The slot opening further defines an acceleration zone and a deceleration zone to meter the flow of cooling fluid within the airfoil.

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can further comprise a leading edge cooling circuit defined by a supply passage, a pin bank passage divided into one or more sub-circuits by pin banks disposed within the pin bank passage, and at least first and second cooling passages. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.

Abstract: An engine comprises an airfoil having at least one internal cooling circuit extending radially from the longitudinal axis of the engine. The cooling circuit is defined by at least one rib extending across an interior of the airfoil and at least one internal wall defining an internal passage. The internal wall further defines one or more near wall cooling passages. A thermal stress reduction structure is provided between the rib and the internal wall, providing efficient cooling at a junction between the rib and the internal wall.

Abstract: A turbine engine comprises an airfoil having one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.

Abstract: A turbine engine can include an airfoil comprising an outer wall bounding an interior, as well as an airfoil cooling circuit located within the interior and including a feed tube separating into at least first and second branches. A flow divider can be included in the airfoil and positioned to confront the feed tube.

Abstract: An apparatus and method for an airfoil for a gas turbine engine includes a trailing edge cooling circuit utilizing a plurality of trailing edge ejection holes. The ejection holes can include a circumferentially radiused inlet, a converging section, a metering section, and a diverging section to improve airfoil cooling as well as castability.

Abstract: A turbine engine comprises an airfoil having one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can further comprise a leading edge cooling circuit defined by a supply passage, a pin bank passage divided into one or more sub-circuits by pin banks disposed within the pin bank passage, and at least first and second cooling passages. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.

Abstract: An airfoil for a gas turbine engine can receive a flow of cooling fluid through a cooling circuit. The cooling circuit is defined within the airfoil comprising a supply passage and a leading edge cooling passage, the two passages being in fluid communication through a plurality of impingement orifices disposed within a cross-over rib disposed between and at least partially defining the passages. The cross-over rib can further comprise a cross-section to provide thermal stress-relief for the cross-over rib.